US10041443B2 - Thrust reverser apparatus and method - Google Patents

Thrust reverser apparatus and method Download PDF

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Publication number
US10041443B2
US10041443B2 US14/734,298 US201514734298A US10041443B2 US 10041443 B2 US10041443 B2 US 10041443B2 US 201514734298 A US201514734298 A US 201514734298A US 10041443 B2 US10041443 B2 US 10041443B2
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United States
Prior art keywords
blocker door
thrust reverser
blocker
translating sleeve
pivot joint
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US14/734,298
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English (en)
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US20160363097A1 (en
Inventor
David W. Foutch
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Boeing Co
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Boeing Co
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Publication date
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Priority to US14/734,298 priority Critical patent/US10041443B2/en
Assigned to THE BOEING COMPANY reassignment THE BOEING COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FOUTCH, DAVID W.
Priority to CA2922304A priority patent/CA2922304C/en
Priority to JP2016039744A priority patent/JP6742114B2/ja
Priority to EP16169757.8A priority patent/EP3103995B1/en
Priority to CN201610406005.3A priority patent/CN106246409B/zh
Publication of US20160363097A1 publication Critical patent/US20160363097A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/766—Control or regulation of thrust reversers with blocking systems or locking devices; Arrangement of locking devices for thrust reversers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y02T50/671—

Definitions

  • the present disclosure relates generally to aircraft, and more particularly to a thrust reverser apparatus configured for use on aircraft.
  • control devices are used to effectively and efficiently maneuver aircraft during various phases of flight.
  • Some control devices are directly attached to wings of aircraft, such as ailerons adapted for controlling “roll”, i.e. rotational movement of an aircraft about its longitudinal axis.
  • Spoilers may also be directly attached to aircraft wings to rapidly reduce wing lift when and as desired, particularly during various descent phases of a flight.
  • Flaps are typically attached directly to the wings to change their aerodynamic shapes for assuring stable flight control during slower speeds, such as during takeoff and landing.
  • thrust reverser Upon landing of a commercial jet aircraft, some form of thrust reverser is generally deployed immediately after actual touchdown to reduce rolling groundspeed to a point where landing gear wheel braking becomes effective.
  • a two-piece clam-style thrust reverser is typically deployed from the engine exhaust outlet to direct exhaust thrust forwardly for retarding groundspeed.
  • the thrust reverser is typically situated within an annular bypass air duct situated between the engine and engine nacelle, in the form of a circumferential ring of blocker doors attached to linkage configured to deploy the doors into the duct.
  • Such components for example the blocker doors and their deployment mechanisms, should be lighter in weight, ideally possess enhanced functionality such as allowing for more noise abatement surface area, and yet maintain required strength and robustness in the face of increasingly stringent design targets.
  • a thrust reverser for a turbofan engine including an engine core and a nacelle defining an axially extending bypass duct for receiving a fan bypass air stream, includes an axially translating sleeve movably coupled to a fixed portion of the nacelle and thereby to the engine fan case.
  • Blocker doors having an axial orientation when in a stowed position are pivotally coupled to the translating sleeve.
  • An outer wall of the bypass duct is radially interposed between the blocker doors and the fan bypass air stream when the blocker doors are the stowed position.
  • each blocker door is coupled to the translating sleeve at a first pivot joint, and each blocker door is configured to pivot radially inwardly about the first pivot joint to a deployed position in which the blocker door is disposed at least partially in the fan bypass air stream.
  • a drag linkage is coupled to each blocker door at the second pivot joint fixed at an intermediate location along a length of each blocker door.
  • a blocker door brake is configured to prevent rotation of the blocker door about the second pivot joint when the blocker door brake is engaged.
  • another embodiment of the disclosed thrust reverser has sets of dual blocker doors and eliminates the need for cascade sets, while also providing a radially interposed axially extending outer wall of the annular bypass duct between the blocker doors and the fan bypass air stream when the thrust reversed has been stowed.
  • FIG. 1 is a schematic side view of a turbofan engine nacelle, of a type utilized on a commercial aircraft that may incorporate a thrust reverser configured in accordance with this disclosure, showing the thrust reverser in its fully deployed position.
  • FIG. 2 is a schematic side view taken along lines 2 - 2 of FIG. 1 , depicting the disclosed thrust reverser in its fully deployed position.
  • FIG. 3 is a schematic side view similar to that of FIG. 2 , but with the disclosed thrust reverser depicted in its fully stowed position, both removed and concealed from a turbofan bypass duct and associated air flow, respectively.
  • FIG. 4 is a schematic side view similar to that of FIGS. 2 and 3 , but with the disclosed thrust reverser depicted in an intermediate position; i.e. between fully deployed and fully stowed positions of FIGS. 2 and 3 , respectively.
  • FIG. 5 is a flowchart depicting an exemplary deployment sequence of one embodiment of the present disclosure.
  • FIG. 6 is a schematic side view of an alternate embodiment of the disclosed thrust reverser, shown in a fully deployed position.
  • FIG. 7 is a schematic side view of the same alternative embodiment of the disclosed thrust reverser, shown in a stowed position.
  • FIG. 1 is a schematic view of a turbofan nacelle 14 secured to a turbofan engine (not shown) attached to a pylon 12 of a type typically supported from an aircraft wing (not shown).
  • the turbofan engine (hidden) is enclosed by the nacelle 14 .
  • the nacelle 14 includes a fixed portion 15 , and a translating sleeve assembly 16 , configured to uncover a series of translating cascade sets 20 , each of which includes a plurality of forwardly-directed vanes 19 configured to provide reverse thrust.
  • Reverse thrust is achieved by the vanes 19 , which are angled to redirect air passing through an axially extending bypass duct 22 ( FIG. 2 ) in a forward direction to reverse the otherwise aft movement of a fan bypass air stream 32 ( FIG. 2 ) to be described.
  • the plurality of cascade sets 20 are circumferentially arranged as spaced islands that define spaces 24 between adjacent cascade sets 20 .
  • the cascade sets 20 essentially form a circumferential “cascade basket”, and within one or more of each space 24 is situated a telescopically extensible and retractable (or collapsing) first and second hydraulic cylinders 25 , 26 ( FIG. 2 ), configured to deploy a thrust reverser 28 both axially and radially into the bypass duct 22 , as will be described herein.
  • an actuation system 29 can be used for moving the thrust reverser 28 between stowed and deployed positions.
  • the thrust reverser is shown fully deployed.
  • the actuation system 29 includes actuator heads 30 , fixed to a conic structure 31 , which in turn is fixed to a forward fixed portion 15 of the nacelle 14 .
  • the conic structure 31 also interfaces with an outer wall 50 of the annular-shaped bypass duct 22 through a V-blade/V-groove arrangement (not shown).
  • a non-telescoping base cylinder 27 is directly affixed to each actuator head 30 for receiving the first and second retractable cylinders 25 , 26 in a nested configuration when retracted, as will be appreciated by those skilled in the art.
  • the actuation system 29 includes at least the actuator head 30 , its associated base cylinder 27 , and telescoping cylinders 25 , and 26 .
  • a plurality of fan blades 34 forces the fan bypass air stream 32 through the bypass duct 22 .
  • the fan bypass air stream 32 passes from the fan blades 34 through stator vanes 36 , for assuring desired directional control of the fan bypass air stream 32 .
  • a fan blade containment ring 35 situated about the periphery of the fan blades 34 and comprising a portion of a forward fan case 52 , is configured to minimize risk of any failed fan blade parts or pieces actually separating from the turbofan engine and piercing through and escaping the nacelle 14 .
  • the thrust reverser 28 may be fully deployed to the position shown in FIG. 2 , in which blocker doors 40 physically redirect the fan bypass air stream 32 into a circumferentially outward direction through the cascade sets 20 to produce the described reverse thrust effect.
  • the blocker doors 40 serve to block the bypass air stream 32 from exiting the rear 23 of the bypass duct 22 , as otherwise occurs during normal flight.
  • deployment of the thrust reverser 28 is initiated via the actuation system 29 , which is fixed to the nacelle 14 and to the translating sleeve assembly 16 .
  • the actuation system 29 is configured to extend the translating sleeve assembly 16 axially from a fully stowed position to a fully deployed position, and to alternately retract the translating sleeve assembly 16 from a fully deployed position to a fully stowed position.
  • the actuation system 29 causes each actuator head 30 to extend its respective retractable hydraulic cylinders 25 , 26 , in turn translating axially rearward the cascade sets 20 and the blocker doors 40 , along with associated drag linkage 42 by which the blocker doors are pivotally connected to the cascade sets 20 , as further described below.
  • the thrust reverser 28 When the thrust reverser 28 is in a fully deployed state ( FIG. 2 ), the blocker doors 40 are completely extended and angled radially inwardly to contact, or come into close proximity with, the circumferential exterior 38 of a jet engine core cowl 18 as shown, to block the fan bypass air stream 32 from exiting through the rear 23 of the duct 22 as earlier noted.
  • the thrust reverser 28 is shown in a fully stowed position in FIG. 3 , as contrasted to FIG. 2 in which the thrust reverser 28 is shown in its fully deployed position.
  • all noted components of the thrust reverser 28 including the cascade sets 20 and the hydraulic cylinders 25 , 26 , are shown in their retracted states.
  • each of the telescoping cylinders 25 , 26 is retracted into its associated non-telescoping base cylinder 27 , each of the latter being rigidly fixed to one of the actuator heads 30 .
  • an interior wall 54 of the translating sleeve assembly 16 may be formed with apertures, perforations, and/or otherwise treated with known acoustical dampening materials to facilitate compliance with noise abatement protocols.
  • a first phase of thrust reverser deployment involves its movement from the stowed position shown in FIG. 3 to the intermediate position shown in FIG. 4 .
  • the hydraulic actuator system 29 actuates each actuator head 30 to first extend the first hydraulic cylinder 25 associated with that respective head 30 , causing the cascades 20 , blocker doors 40 , drag linkages 42 , and the translating sleeve assembly 16 , to all move axially aft or rearward.
  • one or more blocker door brakes 46 and one or more track locks 48 are operated as follows.
  • both the blocker door brake 46 and the track lock 48 are engaged.
  • the track lock when engaged, prevents the translating sleeve assembly 16 from moving along a slider track 49 .
  • a blocker door brake 46 when engaged, holds the drag linkage 42 to the cascade 20 , thereby preventing motion of the drag linkage 42 that would deploy the blocker door 40 radially inward.
  • the track lock 48 is first released to initiate deployment of the thrust reverser 28 from the stowed position.
  • the actuator heads 30 then move the translating sleeve assembly 16 , together with the cascades 20 , blocker doors 40 and drag linkages 42 , aft or rearward via the extension of the first hydraulic cylinder 25 , as shown in FIG. 4 during the initial phase of thrust reverser deployment.
  • the track lock 48 is then engaged, i.e. locked. This completes the first phase of the thrust reverser deployment.
  • a second phase of the thrust reverser deployment involves releasing the blocker door brake 46 , and extending the second hydraulic cylinder 26 , causing the cascades 20 to move further aft and to cause deployment of the blocker doors 40 into the bypass duct 22 (as shown in FIG. 2 ).
  • pivot joints 56 , 60 , 44 allow each drag linkage 42 and associated blocker door 40 to move from positions shown in FIG. 4 to their respective positions shown in FIG. 2 .
  • the pivot joint 56 is affixed to the aft end 58 of each blocker door 40 and to the translating sleeve assembly 16 .
  • the pivot joint 60 is affixed to the forward end of each drag linkage 42 and to the forward end of the cascade 20 .
  • the pivot joint 44 is located approximately midway along the blocker door 40 and is affixed to the blocker door 40 and to the drag linkage 42 .
  • each actuator head 30 causes each actuator head 30 to extend each second hydraulic cylinder 26 .
  • the aft end of each second hydraulic cylinder 26 is affixed to an end of a cascade 20 .
  • each second hydraulic cylinder 26 extends, it causes its associated cascade 20 to move along its associated slider track 49 .
  • This motion also simultaneously causes the forward portion of each drag linkage 42 to pivot about its pivot joint 60 , the aft portion of the drag linkage 42 to pivot about its pivot joint 44 , and the aft end 58 of each blocker door 40 to pivot about its pivot joint 56 .
  • the pivot joints 56 , 60 and 44 cooperating together with the drag linkage 42 , the blocker door 40 and the cascade 20 , all move on a respective slider track 49 from positions shown in FIG. 4 to their respective positions in FIG. 2 , via extension of the second hydraulic cylinder 26 .
  • the second hydraulic cylinder 26 is fully extended, the second phase of the thrust reverser deployment is complete, and the thrust reverser is in its fully deployed position, with the blocker doors 40 blocking the bypass duct 22 , causing the bypass duct airflow 32 to be diverted through the cascades 20 .
  • FIG. 5 is a flowchart depicting a deployment sequence for the described embodiment of the thrust reverser 28 , including steps as referenced below:
  • Retraction of the thrust reverser 28 is also initiated by the actuator system 29 , which causes each actuator head 30 to retract each second hydraulic cylinder 26 , causing the blocker doors 40 to retract radially out of the fan bypass air stream 32 , similar to the action of an umbrella being collapsed and folded inwardly toward its telescopically retractable handle.
  • the blocker door brake 46 is engaged again, the track lock 48 is released, and each first hydraulic cylinder 25 retracts forwardly, in turn pulling the cascade sets 20 and translating sleeve assembly 16 forwardly into their fully stowed positions, shown in FIG. 3 .
  • the track lock 48 Upon full retraction, the track lock 48 is selectively engaged, wherein the thrust reverser 28 is then fully and securely stowed. When fully stowed ( FIG. 3 ), the interior wall 54 of the translating sleeve assembly 16 abuts a bullnose 80 , completely concealing the entire thrust reverser 28 , including all of its components, from the fan bypass air stream 32 .
  • an alternate embodiment of a thrust reverser 28 ′ utilizes a circumferential array of dual blocker doors 40 ′ and 40 ′′, shown schematically in a fully deployed state.
  • the cascade sets 20 of the previously described embodiment are not included, as they are not required.
  • dual sets of the blocker doors 40 ′, 40 ′′ are pivotally connected together via dual pivot joints 56 ′and 56 ′′ to create reverse thrust without such cascade sets.
  • the circumferentially arranged blocker doors 40 ′, 40 ′′ are opened as shown to form a clam-shell style thrust reversing mechanism that also effectively interfaces with the bypass duct 22 to provide the reversing function.
  • the base cylinder 27 ′ contains only one telescoping hydraulic cylinder 26 ′ for deployment of the dual blocker doors, which are each pivotal about respective pivot joints 60 ′ and 60 ′′ on the aft end of the hydraulic cylinder 26 ′, as shown.
  • the thrust reverser 28 ′ is also configured so that when in the retracted and stowed position, it is concealed behind the outer wall 50 of the bypass duct 22 .
  • the actuator system 29 ′ includes an actuator head 30 ′, a base cylinder 27 ′ attached to the actuator head 30 ′, and the single extensible cylinder 26 ′.
  • Deployment of the thrust reverser 28 ′ is also achieved in two phases, and includes telescopic extension of the cylinder 26 ′ from the base cylinder 27 ′, wherein during the first phase the blocker doors 40 ′, 40 ′′ remain axially oriented, and are caused to remain axially oriented via engagement of the drag linkage brake 47 ′.
  • the second phase of deployment includes pivoting of the blocker doors 40 ′, 40 ′′ about pivot joints 60 ′ and 60 ′′, for extension of the doors into the fan bypass air stream 32 . This occurs after the drag linkage brake 47 ′ has been released.
  • there are no translating cascade sets 20 as in the first described embodiment of the thrust reverser 28 (see especially FIGS. 2-4 ).
  • thrust reverser structures as described herein may offer numerous benefits over related art. Not only may a weight penalty be avoided, but the above-described structures may also be configured to substantially reduce excrescence drag. Among additional benefits are reductions in manufacturing complexity, compared to related art thrust reverser assemblies, and avoidance of inherent drag issues associated with related art thrust reverser structures that remain within the fan bypass air stream even while stowed during flight.
  • the disclosure may cover numerous embodiments not described herein.
  • specific dimensions of the blocker doors and drag linkages may be tailored and/or adjusted to support various aerodynamically distinct bypass air stream geometries for minimizing excrescence drag coefficients, including those related to skin surface friction, parasitic and separation drag, as well as wave drag.
  • particular forms and shapes of the components may be adjusted to optimize thrust reverser performance characteristics.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Retarders (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US14/734,298 2015-06-09 2015-06-09 Thrust reverser apparatus and method Active 2036-07-21 US10041443B2 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US14/734,298 US10041443B2 (en) 2015-06-09 2015-06-09 Thrust reverser apparatus and method
CA2922304A CA2922304C (en) 2015-06-09 2016-03-01 Thrust reverser apparatus and method
JP2016039744A JP6742114B2 (ja) 2015-06-09 2016-03-02 逆推力装置及び方法
EP16169757.8A EP3103995B1 (en) 2015-06-09 2016-05-16 Thrust reverser apparatus and method
CN201610406005.3A CN106246409B (zh) 2015-06-09 2016-06-08 推力反向器及其展开方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/734,298 US10041443B2 (en) 2015-06-09 2015-06-09 Thrust reverser apparatus and method

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US20160363097A1 US20160363097A1 (en) 2016-12-15
US10041443B2 true US10041443B2 (en) 2018-08-07

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US (1) US10041443B2 (zh)
EP (1) EP3103995B1 (zh)
JP (1) JP6742114B2 (zh)
CN (1) CN106246409B (zh)
CA (1) CA2922304C (zh)

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US11255293B2 (en) * 2019-04-04 2022-02-22 Airbus Operations Sas Turbofan comprising a nacelle equipped with a reverser system and a mobile cascade grill
EP4163487A3 (en) * 2021-10-05 2023-07-05 Rohr, Inc. Thrust reverser system with hidden turning door
US11840987B2 (en) 2022-04-05 2023-12-12 General Electric Company Cascade thrust reverser assembly for a gas turbine engine
US11913406B2 (en) 2020-04-07 2024-02-27 Rohr, Inc. Hidden door thrust reverser system for an aircraft propulsion system
US12000359B2 (en) 2022-08-18 2024-06-04 General Electric Company Cascade thrust reverser actuation assembly for a turbofan engine

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US10309343B2 (en) * 2014-11-06 2019-06-04 Rohr, Inc. Split sleeve hidden door thrust reverser
US9915226B2 (en) * 2015-06-18 2018-03-13 Rohr, Inc. Variable area fan nozzle hidden blocker door thrust reverser
JP2018530694A (ja) * 2015-09-09 2018-10-18 エムアールエイ・システムズ・エルエルシー スラストリバーサアセンブリ
US10533519B2 (en) * 2016-01-13 2020-01-14 Rohr, Inc. Translating cascade hidden blocker door thrust reverser
US10655564B2 (en) * 2016-05-13 2020-05-19 Rohr, Inc. Thrust reverser system with hidden blocker doors
US20180023509A1 (en) * 2016-07-25 2018-01-25 United Technologies Corporation Thrust reverser structure mounted to fan case
FR3055669B1 (fr) * 2016-09-05 2018-09-28 Airbus Operations Systeme d'inverseur de poussee limitant les perturbations aerodynamiques en configuration inactive
FR3059368A1 (fr) * 2016-11-28 2018-06-01 Airbus Operations Nacelle d'un turboreacteur comportant un volet inverseur
US10227951B2 (en) * 2017-02-02 2019-03-12 Woodward, Inc. Limited flow thrust reverser actuating
FR3062637B1 (fr) * 2017-02-07 2020-07-10 Airbus Operations (S.A.S.) Nacelle de turboreacteur comportant un mecanisme d'entrainement d'inverseur de poussee
FR3064307B1 (fr) * 2017-03-22 2019-03-29 Airbus Operations Nacelle d'un turboreacteur comportant un volet inverseur
FR3064308B1 (fr) * 2017-03-23 2021-06-11 Airbus Operations Sas Turboreacteur comportant une nacelle equipee de volets inverseurs
US10724476B2 (en) * 2017-03-27 2020-07-28 Rohr, Inc. Locking apparatus for a thrust reverser translating sleeve
CN108661821B (zh) * 2017-03-31 2022-03-18 Mra系统有限责任公司 反推力器组件及操作方法
FR3067406B1 (fr) * 2017-06-13 2019-07-12 Airbus Operations Systeme d'inverseur de poussee presentant des perturbations aerodynamiques limitees
FR3067760B1 (fr) * 2017-06-14 2019-06-28 Airbus Operations Turboreacteur comportant une nacelle equipee de volets inverseurs
US10436112B2 (en) * 2017-06-26 2019-10-08 The Boeing Company Translating turning vanes for a nacelle inlet
US10119495B1 (en) * 2017-06-28 2018-11-06 General Electric Company System and method of operating a ducted fan propulsion system inflight
US10641207B2 (en) * 2017-07-21 2020-05-05 The Boeing Company Air flow deflector assembly for a thrust reverser system for reducing re-ingestion of reverse efflux air flow and method for the same
US10578055B2 (en) * 2017-08-10 2020-03-03 Mra Systems, Llc Turbine engine thrust reverser stop
US11125157B2 (en) 2017-09-22 2021-09-21 The Boeing Company Advanced inlet design
US10907577B2 (en) * 2017-10-23 2021-02-02 Rohr, Inc. Translating lock for pivot door thrust reverser
US11396854B2 (en) * 2017-10-25 2022-07-26 Rohr, Inc. Hinge mechanism for pivot door thrust reversers
FR3074854B1 (fr) * 2017-12-08 2020-09-11 Airbus Operations Sas Turboreacteur comportant une nacelle equipee d'un systeme inverseur comportant des portes
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EP3103995B1 (en) 2020-04-01
CA2922304A1 (en) 2016-12-09
CN106246409B (zh) 2020-09-22
JP6742114B2 (ja) 2020-08-19
JP2017002890A (ja) 2017-01-05
CA2922304C (en) 2020-02-18

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